US7555893B2 - Aircraft propulsion system - Google Patents
Aircraft propulsion system Download PDFInfo
- Publication number
- US7555893B2 US7555893B2 US11/336,828 US33682806A US7555893B2 US 7555893 B2 US7555893 B2 US 7555893B2 US 33682806 A US33682806 A US 33682806A US 7555893 B2 US7555893 B2 US 7555893B2
- Authority
- US
- United States
- Prior art keywords
- coil
- fuel cell
- aircraft
- split
- fan
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related, expires
Links
- 239000000446 fuel Substances 0.000 claims abstract description 98
- 239000007788 liquid Substances 0.000 claims abstract description 46
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 41
- 239000001257 hydrogen Substances 0.000 claims abstract description 40
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 40
- 230000005284 excitation Effects 0.000 claims description 41
- 230000002093 peripheral effect Effects 0.000 claims description 12
- 230000003993 interaction Effects 0.000 claims description 4
- 230000007246 mechanism Effects 0.000 abstract description 32
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 18
- 238000010586 diagram Methods 0.000 description 10
- 239000007789 gas Substances 0.000 description 10
- 239000000126 substance Substances 0.000 description 10
- 230000000694 effects Effects 0.000 description 9
- 230000007613 environmental effect Effects 0.000 description 9
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 5
- 230000006872 improvement Effects 0.000 description 5
- 239000007800 oxidant agent Substances 0.000 description 5
- 230000001590 oxidative effect Effects 0.000 description 5
- 229910052710 silicon Inorganic materials 0.000 description 5
- 239000010703 silicon Substances 0.000 description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- 229910002092 carbon dioxide Inorganic materials 0.000 description 4
- 239000001569 carbon dioxide Substances 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- 150000001722 carbon compounds Chemical class 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 230000006698 induction Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000009835 boiling Methods 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 150000002431 hydrogen Chemical class 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000002803 fossil fuel Substances 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
- H02K7/1807—Rotary generators
- H02K7/1823—Rotary generators structurally associated with turbines or similar engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K55/00—Dynamo-electric machines having windings operating at cryogenic temperatures
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to an aircraft propulsion system, and particularly to an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment.
- the optimum thrust, thrust vector, and sectional area for the engine are required in various flight conditions of an aircraft engine, such as take-off, cruise and landing conditions. For example, maximum thrust is required in a take-off condition, or thrust for increasing a direction of braking is required in a landing condition, whereas in a cruise condition are not required low air resistance.
- High bypass-ratio turbofan engines which are used for many highly efficient civil aircraft engines, have large air inlet sectional area (engine sectional area), and do not require thrust during high-speed cruise as much as during take-off, thus the excessively large sectional area of the engine increases the resistance of the aircraft, resulting in a negative impact on the flight performances.
- an afterburner may be mounted in a rear portion of the engine to reduce the outer diameter of the fan, but actuation of the afterburner causes tremendous noise, and thus is not desirable in terms of the engine operation efficiency.
- it is difficult to realize the optimum engine disposition and engine sectional area for all the flight conditions.
- it is of great benefit in aircraft traffic to deflect the thrust vector of aircraft engines, and the various ideas of the deflection have been proposed, thereby some of them are already in use.
- Japanese Patent Application Laid-Open No. 2003-137192 (Title of the invention: “Vertical take-off and landing aircraft”, Date of laid-open publication: May 14, 2003) discloses a turbofan engine where thrust vector is made variable.
- mechanisms of moving engines, or thrust vectoring nozzles for deflecting nozzles are beneficial for military-aircraft use where prompt change in thrust vector in aircraft traffic, but are not so beneficial for the use of civil aircraft the majority of which have large bodies.
- Civil aircraft require thrust vectoring particularly during take-off and landing.
- existing techniques for take-off conditions include a high-lift device which utilizes Coanda effect for the exhaust from the engine which is mounted below the wing by lowering the flap of a rear end of a wing in order to achieve increase of the lift force, and a method of achieving creation of lift force from deflection of the engine itself seen in a VTOL airplane, and of obtaining upward lift force by directing the fan upward during take-off, upon reception of air supplied by an air supply.
- H11-200888 (Title of the invention: “Fuel cell turbine engine”, Date of laid-open publication: Jul. 27, 1999) discloses a fuel cell turbine engine which drives the motor by means of a fuel cell, drives the turbine by means of the motor, and drives the fan by means of output power of the turbine.
- the present invention is contrived in view of the above problems of the conventional technologies, and an object of the present invention is to provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment.
- an aircraft propulsion system comprises a first propulsion unit which generates thrust and a second propulsion unit which has thrust vectoring means for varying a vector of the thrust, wherein the second propulsion unit is an electromagnetic driving fan in which an armature coil is disposed on an outer circumference of the fan, and an excitation coil is disposed on an inner peripheral surface of a casing portion of the fan so as to face the armature coil, and which is driven by electromagnetic force generated by a mutual induction effect between the armature coil and the excitation coil.
- the second propulsion unit is an electromagnetic driving fan in which an armature coil is disposed on an outer circumference of the fan, and an excitation coil is disposed on an inner peripheral surface of a casing portion of the fan so as to face the armature coil, and which is driven by electromagnetic force generated by a mutual induction effect between the armature coil and the excitation coil.
- the second propulsion unit is an electromagnetic driving fan which is drive by electromagnetic force generated by a mutual induction effect between the armature coil and the excitation coil, and doest not require chemical fuel as the energy source, thus the total amount of exhaust containing harmful substances is preferably reduced.
- the armature coil is disposed on an outer circumference of the fan, heavy parts such as an iron core and the like are not necessary, whereby the weight can be reduced.
- large torque can be obtained with electromagnetic force that is produced by a mutual induction effect, thus the outer diameter of the fan can be enlarged. Accordingly, the thrust can be increased and the bypass ratio can also be increased, whereby noise reduction is achieved.
- the electromagnetic driving fan does not require a core engine, and has a simple configuration.
- a flexible line can be employed as the power supply line and thus, the mechanism for varying a thrust vector is not affected negatively. Accordingly, environmental compatibility is improved while securing the optimum thrust and thrust vector for flight conditions of the aircraft.
- the aircraft propulsion system comprises storage means for storing the second propulsion unit in a wing or folding the unit at an external surface of the wing, and wing moving means for moving the second propulsion unit with respect to a width direction of the wing and a wing chord direction.
- the second propulsion unit can be stored in a wing during high-speed cruise, thus the frontal projected area of the airframe is reduced, whereby the air resistance to the airframe can be reduced.
- the second propulsion unit can be moved with respect to a width direction of the wing or a wing chord direction and thus, for example by disposing the second propulsion unit coaxially with respect to the first propulsion unit, the bypass ratio of the first propulsion unit can be increased significantly, and further the noise level at discharging the exhaust gas from the first propulsion unit can be reduced significantly. Therefore, environmental compatibility can be improved while securing the optimum sectional area for the engine in accordance with the flight conditions of the aircraft.
- the first propulsion unit or the second propulsion unit comprises electrical output generating means.
- electric power which is generated by the electrical output generating means, can be supplied preferably to the electromagnetic driving fan which is the second propulsion unit. Accordingly, an operational ratio of the electromagnetic driving fan can be increased, as a result of which the ratio of the chemical fuel in the power source can be reduced and the ratio of the electrical energy can be increased, hence the total amount of exhaust containing harmful substances is reduced.
- the electrical output generating means is an aircraft generator, a fuel cell, or a combination thereof with an electrical accumulator.
- a fuel cell or combination of the aircraft generator and fuel cell with an actuator can recharge the battery while producing electric power efficiently.
- the ratio of the chemical fuel as the power source can be reduced and the ratio of the electrical energy can be increased, hence the total amount of exhaust containing harmful substances is reduced.
- the first propulsion unit and the fuel cell use liquid hydrogen as fuel.
- liquid hydrogen is the fuel, thus the combustion temperature is reduced by steam which is produced as a result of combustion of the liquid hydrogen with air.
- generation of nitrogen oxides can be controlled preferably, and, since the fuel does not contain carbon, carbon compounds such as carbon dioxide can be prevented from being exhausted, whereby environmental compatibility is improved significantly.
- the aircraft propulsion system comprises means in which the liquid hydrogen brings the armature coil and the excitation coil to a superconductive state and is vaporized by receiving heat from the first propulsion unit or the second propulsion unit.
- the armature coil and the excitation coil are brought to a superconductive state by the liquid hydrogen. Accordingly, the internal resistance to the coils become small as much as possible, almost no electric power is consumed when the electromagnetic driving fan as the second propulsion unit is driven, whereby the energy efficiency is improved significantly. Moreover, heat that is equivalent to heat of vaporization of the liquid hydrogen is drawn from exhaust, whereby the temperature of the exhaust is reduced, as a result of which generation of nitrogen oxides is controlled preferably.
- the fuel cell is disposed between a compressor and a combustor that configure the first propulsion unit.
- compressed air can be supplied to an oxidant electrode of the fuel cell, and vaporized hydrogen gas can be supplied to the both fuel cell and the combustor. Accordingly, the electrical efficiency of the fuel cell and combustion efficiency of the combustor are simultaneously enhanced.
- the second propulsion unit comprises means or increasing input pressure of the fuel cell.
- the electrical efficiency of the fuel cell is improved significantly.
- FIG. 1 is an explanatory diagram of a configuration, showing the aircraft propulsion system of an embodiment of the present invention
- FIG. 2 is a front view showing a main part of the electromagnetic driving fan of the embodiment
- FIG. 3 is an explanatory diagram showing a two-dimensional relative position of a coil A i row or coil B i row with respect to a coil M i row;
- FIG. 4 is an explanatory diagram showing an applicable example for an aircraft of the aircraft propulsion system of the present invention
- FIG. 5 is an explanatory diagram showing a electrical generator as the electrical output generating means of the aircraft propulsion system of the present invention.
- FIG. 6 is an exemplifying diagram showing an operation of pressure increasing means of an air inlet of the fuel cell.
- FIG. 1 is an explanatory diagram of a configuration, showing an aircraft propulsion system 100 of an embodiment of the present invention.
- the aircraft propulsion system 100 comprises a turbo fan engine 1 , 1 as a first propulsion unit for generating thrust, an electromagnetic driving fan 10 , 10 as a second propulsion unit, a rotating mechanism portion 2 , 2 as thrust vectoring means for vectoring a thrust vector of the electromagnetic driving fan, a slide mechanism portion 3 , 3 as wing moving means for moving the electromagnetic driving fan with respect to a width direction of the wing and a wing chord direction, a storage mechanism portion 4 , 4 as storage means for storing the electromagnetic driving fan in a wing or an external surface of the wing, a liquid fuel line 5 , 5 which supplies liquid hydrogen which is provided as fuel in the turbofan engine while cooling each coil of the electromagnetic driving fan, a heat exchanger 6 , 6 in which exhaust from the turbofan engine and the liquid fuel exchange heat with each other, a generating portion 7 , 7 as electrical output generating means of the turbofan engine, and an accumulating portion 8 , 8 which accumulates electric power produced from a fuel cell.
- the heat exchanger 6 6
- the rotating mechanism portion 2 is configured by combining, for example, an axis of rotation with a rotating machine.
- the rotating machine may be of electric motor-driven type or hydraulic type.
- the slide mechanism portion 3 is configured by combining, for example, a plurality of reciprocating machines.
- the reciprocating machines may be of electric motor-driven type or hydraulic type.
- the storage mechanism portion 4 is configured by combining, for example, a hinge with the rotating machine.
- the rotating machine may be of electric motor-driven type or hydraulic type.
- liquid hydrogen as the fuel flows therein and cools an armature coil and excitation coil of the electromagnetic driving fan 10 to bring them into a superconductive state. Thereafter, the liquid hydrogen is vaporized after receiving the heat energy from exhaust discharged from the turbofan 1 in the heat exchanger 6 . Some of the vaporized hydrogen is provided inside a combustor of the turbofan 1 , and the rest is provided to a fuel side electrode of the fuel cell. Although not shown, the liquid hydrogen is, for examples, stored in a cryogenic apparatus.
- a narrow tube is embedded in an exhaust nozzle of the turbofan 1 .
- the electromagnetic driving fan 10 is disposed in each of the wings, but a configuration is possible in which another electromagnetic driving fans 10 is disposed ahead of the axis of the turbofan engine 1 resulting in two electromagnetic driving fans 10 , 10 disposed on each of the wings.
- the electromagnetic driving fan is light in terms of weight, and has a simple configuration. Therefore, a thrust vectoring mechanism, storage mechanism, and wing moving mechanism can be realized easily, and the optimum thrust and thrust vector can be secured in accordance with the flight conditions, as well as the optimum sectional area of the engine.
- FIG. 2 is a front view showing a main part of the electromagnetic driving fan 10 of the embodiment.
- the split excitation coils change the roles thereof in accordance with a relative position with respect to the coil M i .
- the split excitation coil when the split excitation coil overlaps with a central portion of the coil M i , the split excitation coil supplies an effective magnetic field related to the abovementioned effective electromagnetic force to the coil M i , and, when the split excitation coil overlaps with either one of end portions of the coil M i , the split excitation coil applies effective induced current related to the effective electromagnetic force to the coil M i .
- the coil A i is for the case in which an effective magnetic field related to the effective electromagnetic force is formed in the coil M i
- the coil B i is for the case in which effective induced current related to the effective electromagnetic force is applied to the coil M i ; however, the coil A i and the coil B i are exactly the same coils in terms of the structure, thus the split excitation coils may be the coil A i and the coil B i .
- the dual liquid fuel lines 5 , 5 that one is inlet line and the other outlet line are connected to the fan blade 11 and the fan casing 33 respectively, wherein liquid hydrogen supplied from the inlet liquid fuel supply line 5 circulates and cools the coil A i row, coil B i row, and coil M i to bring them to a superconductive state. Thereafter, the liquid hydrogen is provided to the heat exchanger 6 of the turbofan engine 1 while flowing in the outlet liquid fuel supply line 5 , and exchanges heat with the exhaust. The liquid fuel is then vaporized and provided to the fuel side electrode of the fuel cell and the combustor of the turbofan engine 1 .
- the width length of the coil M i is set as L 1
- the width length of the coil A i or the coil B i is set as L 2 , which is abbreviated as L 1 /2.
- the abovementioned effective magnetic field is one of magnetic fields formed in the split armature coils by the split excitation coils, and is a cause of generation of the effective electromagnetic force.
- the abovementioned effective induced current is one of induced currents applied to the split armature coils by the split excitation coils, and is a cause of generation of the effective electromagnetic force.
- the current control device 44 relates to control of current for the coil A i row and the coil B i row, and performs control of current on, for example, a combination of a plurality of continuous coils A and coils B, or, for example, a group of a coil A i , coil B i , coil A i+1 , and coil B i+1 .
- FIG. 3 is an explanatory diagram showing a two-dimensional relative position of a coil A i row or coil B i row with respect to a coil M i row.
- This figure shows a state in which the coil M i row is projected onto the inner peripheral surface of the fan casing 33 , and the inner peripheral surface of the fan casing 33 is unrolled to be shows as a two-dimensional flat surface.
- the coil A i row or the coil B i row is disposed on the inner peripheral surface of the fan casing 33 , thus they rest with respect to the coil M i row.
- the coil M i row is disposed on the outer circumference of the fan blade 11 , thus it moves with respect to the coil A i row or the coil B i row.
- the coil A i or coil B i is a, for example, single-wound or compound-wound split excitation coil in the form of a rectangle, and comprises a condenser C which constitutes an LC circuit at an end portion of each coils in conjunction with the coil A i or coil B i , a first and a second silicon controlled rectifier SCR 1 and SCR 2 which conduct current to the coil A i or coil B i in two directions, a switching circuit SW which switches the bias direction of the condenser C in accordance with the polarity of the condenser C, and a power source S which supplies an electrical charge to the condenser C.
- a condenser C which constitutes an LC circuit at an end portion of each coils in conjunction with the coil A i or coil B i
- a first and a second silicon controlled rectifier SCR 1 and SCR 2 which conduct current to the coil A i or coil B i in two directions
- a switching circuit SW which switches the bias direction of
- switching control of the first and second silicon controlled rectifier SCR 1 and SCR 2 and the switching control of the switching circuit SW are performed by the current control device 44 on the basis of information from the position detection sensor which shows a position of rotation of the coil M i .
- the coil A i and the coil B i have in common in terms of contribution to generation of effective electromagnetic force for rotating the fan blade 11 with respect to the coil M i .
- the roles of the coil A i and the coil B i are completely different in terms of the mechanism that the coil M i generates the effective electromagnetic force.
- the coil A i plays a role of providing the coil M i with an effective magnetic field related to effective electromagnetic force
- the coil B i plays a role of applying the coil M i with effective induced current related to the effective electromagnetic force.
- Reactive induced current which is applied to the coil M i by the coil A i and does not contribute to rotation of the fan blade 11 is canceled out preferably due to the characteristics of the structure of the coil M i , and reactive electromagnetic force, which is produced by reactive magnetic field which is provided to the coil M i by the coil B i and does not contribute to the rotation of the fan blade 11 , is also canceled out.
- the coil A i or the coil B i configure the LC circuit along with the condenser C
- current that flows into the coil A i or the coil B i when the silicon controlled rectifiers are switched on is current which changes in time, or so-called alternating current.
- alternating current flows in the coil A i or coil B i as excitation current
- a magnetic field which is formed by the excitation current and penetrates through the coil M i also changes in time. Therefore, the time change of the magnetic field causes induced current to flow in the coil M i in a direction of preventing the magnetic field from being changed in time. Accordingly, current can be allowed to flow in the coil M i , which is an armature coil, without supplying current from outside.
- the coil M i is a figure-of-eight coil which crosses and forms symmetry at a central portion, and, for convenience of explanation, may be a single-wound or compound-wound coil. Because the coil M i crosses, for example, the induced currents applied to the coil M i by the coil A i are canceled out with each other at the central portion, as a result of which the coil A i provides the coil M i with only an effective magnetic field related to the effective electromagnetic force which contributes to rotation of the fan blade 11 . On the other hand, the induced currents applied to the coil M i by, for example, the coil B i and coil B i+1 respectively flow in the same direction at the central portion, and electromagnetic force generated by the induced currents is added.
- the directions of magnetic fields formed in the coil M i+1 by the coil B i and coil B i+1 at both end portions of the coil M i are opposite to each other, and the induced currents flow in the same direction, thus electromagnetic force generated by the interaction between the magnetic fields and the induced currents cancel out with each other, as a result of which the coil B i and the coil B i+1 apply the coil M i with only effective induced current related to the effective electromagnetic force. Then, the effective electromagnetic force is generated by the interaction between the effective induced currents and the effective magnetic fields, and the fan blade 11 is rotated by the effective electromagnetic force.
- silicon controlled rectifiers are employed as the switching means in the present embodiment, but semiconductor switching elements such as a power transistor, power MOSFET, IGBT, or the like may be used.
- the power source S is, for example, a secondary battery, and the electric power is supplied by a combination of an aircraft generator as the electrical generator 7 and a fuel cell, a combination of a fuel cell and an electrical accumulator, a single fuel cell, a single electrical accumulator, or a combination of the fuel cell and electrical accumulator.
- the electromagnetic driving fan 10 the electrical energy, which is supplied in order to excite the split excitation coils such as coil B i , coil B i+1 , and the like, is preferably collected and accumulated as the electrical energy again by the condenser C, and the electrical energy is reused by the switching means such as the silicon controlled rectifier in order to excite the split excitation coils again. Therefore, the electromagnetic driving fan 10 has an energy collection function. Moreover, the split armature coils and the split excitation coils are brought to the superconductive state by liquid hydrogen, as will be described hereinafter, and thus have extremely small resistance. Therefore, the electrical energy for exciting the split excitation coils is scarcely consumed in the process of generating the effective electromagnetic force for rotating the fan blade 11 , and the energy efficiency of the electromagnetic driving fan itself is significantly increased.
- FIG. 4 is an explanatory diagram showing an applicable example for an aircraft of the aircraft propulsion system 100 of the present invention.
- the turbofan engine 1 as the first propulsion unit and the electromagnetic driving fan 10 as the second propulsion unit are disposed at each of the wings of the aircraft.
- FIG. 4( a ) for example, in an initial state of take-off in which the aircraft is transferred from a resting state to an accelerating state, a thrust vector of the electromagnetic driving fan 10 is caused to correspond to the traveling direction by the rotating mechanism portion 2 , which is the thrust vectoring means, so that thrust in a horizontal direction is maximized.
- FIG. 4( b ) for example, in an end sate of take-off in which the aircraft receives lift force and takes off, a thrust vector of the electromagnetic driving fan 10 is caused to correspond to the take-off direction by the rotating mechanism portion 2 , which is the thrust vectoring means, by, for example, inclining a rotation angle backward so that thrust in the take-off direction is increased.
- FIG. 4( a ) for example, in an initial state of take-off in which the aircraft is transferred from a resting state to an accelerating state, a thrust vector of the electromagnetic driving fan 10 is caused to correspond to the traveling direction by the rotating mechanism portion 2 , which is the thrust vectoring means, so
- the electromagnetic driving fan 10 for example, in a cruising state in which the aircraft steadily travels at a predetermined altitude or speed, the electromagnetic driving fan 10 is disposed ahead of and coaxially with the turbofan engine 1 by the slide mechanism portion 3 , which is the wing moving means, in order to reduce the air resistance as much as possible, as a result of which a front projected area of the airplane is reduced, and the air resistance to the airplane during cruising is reduced.
- the electromagnetic driving fan 10 is stored in the wing by the storage mechanism portion 4 , which is the storage means, and, as a result, the front projected area of the airplane is reduced, and the air resistance to the airplane during cruising is reduced.
- the storage mechanism portion 4 which is the storage means
- FIG. 5 is an explanatory diagram showing the electrical generator 7 as the electrical output generating means of the aircraft propulsion system of the present invention.
- a fan drive shaft 15 of the turbofan engine 1 is coupled to an aircraft generator 71 , which is rotary driven by output power of a low pressure turbine 14 , whereby electric power is produced.
- the produced electric power is accumulated in the accumulating portion 8 (not shown), e.g. electrical accumulator, and at the same time supplied to the electromagnetic driving fan, other electrical machines, and electronic devices.
- the aircraft generator 71 as the electrical output generating means is coupled to the fan drive shaft 15 of the turbofan 1 , the aircraft generator 71 is then rotary driven by the output power of the low pressure turbine 14 to produce electric power, and at the same time air from a compressor 12 is obtained as an oxidant, and the electric power is produced by a fuel cell 72 which uses liquid hydrogen as fuel.
- the fuel cell 72 is disposed between the compressor 12 and a combustor 13 of the turbofan 1 . Accordingly, compressed air can be supplied to an oxidant electrode of the fuel cell 72 , and the electrical efficiency of the fuel cell 72 is improved.
- the compressed air is extracted from a compressor outlet portion by providing the fuel cell 72 in parallel with the turbofan engine 1 to introduce the extracted compressed air to the oxidant electrode of the fuel cell 72 .
- the electrical output generating means the air from the electromagnetic driving fan 10 is obtained as an oxidant, and the fuel cell 72 using the liquid hydrogen as fuel is combined with the electrical accumulator (not shown).
- the electrical accumulator is what is termed “secondary battery.”
- Liquid hydrogen is used as fuel for the fuel cell and the turbo fan engine.
- the liquid hydrogen is not introduced as liquid to the fuel side electrode of the fuel cell, but, first of all, cools the armature coil and excitation coil of the electromagnetic driving fan 10 to bring them into a superconductive sate. Accordingly, current can be allowed to flow in the armature coil and excitation coil without producing almost no loss of electrical resistance, and the energy efficiency of the electromagnetic driving fan 10 can be improved.
- the liquid hydrogen is introduced to the heat exchanger 6 provided inside the exhaust nozzle. Accordingly, energy of the exhaust is collected as heat energy, and the energy efficiency of the entire system can be improved.
- the liquid hydrogen is provided to the combustor 13 of the turbofan engine 1 and to the fuel side electrode of the fuel cell 72 .
- the hydrogen is combusted and reacts with the compressed air in the combustor, and thereby produces water vapor.
- the vapor reduces combustion temperature, and preferably controls generation of NO x , i.e. nitrogen oxides.
- hydrogen fuel does not contain carbon, and thus does not exhaust carbon dioxide which is a cause of global warming.
- the electric power which is produced by the aircraft generator of the electrical output generating means such as the fuel cell, becomes the drive source for the electromagnetic driving fan 10 , thus an operational ratio of the turbofan engine 1 having the combustor is reduced and an operational ratio of the electromagnetic driving fan 10 is increased, whereby the amount of exhaust containing nitrogen oxide is reduced. Therefore, environmental compatibility is significantly improved, compared to the conventional aircraft propulsion systems which use fossil fuel.
- the electromagnetic driving fan 10 the armature coil is disposed on the outer circumference of the fan, thus large torque can be produced with small size of the force, and the outer diameter of the fan blade 11 can be enlarged.
- the electromagnetic driving fan 10 is disposed ahead of the axis of the turbofan engine 1 by the slide mechanism portion 3 , whereby the bypass ratio of the turbofan engine 1 is increased, and the noise level is reduced.
- the electromagnetic driving fan can secure extremely high efficiency and performance by using a superconductive coil.
- the effectiveness has been observed in a test installation of a magnetically levitated transportation system in the past, but, in a large scale practical test, securing the superconductive state is achieved mainly by means of liquid helium in an extremely low temperature of 4 Kelvin.
- the liquid hydrogen By using the liquid hydrogen as a superconductive drive means, and by performing regenerative heat exchange with engine exhaust heat, the liquid hydrogen is gasified.
- the gasified hydrogen is used as fuel for the gas turbine or fuel cell.
- the fuel cells using hydrogen some are driven at low temperatures.
- a fuel cell of high-temperature operation type can be used to achieve improvement of the heat efficiency by effectively using the gas turbine and heat.
- FIG. 6 is an exemplifying diagram showing an operation of pressure increasing means of an air inlet of the fuel cell.
- FIG. 6 shows an example of the pressure increasing means used in this situation.
- a small boost fan 20 is provided in a coaxial slipstream of the electromagnetic driving fan 10 to increase the pressure at the fuel cell air inlet.
- the blade lattice of the fan by appropriately designing the blade lattice of the fan so that pressurization at an outer peripheral portion where peripheral velocity is high is made larger than an inner peripheral portion, and an air intake port of fuel cell is provided at the slipstream.
- the fuel cell since the blade lattice can be designed easily, the fuel cell is disposed on a periphery at the outer peripheral portion of the fan, but the fuel cell can be provided on an inner side with respect to a central axis of rotation of the fan by providing a vectoring duct introducing the outer air to the center portion.
- the fuel cell discharge high-temperature exhaust in either embodiment. It is possible to contribute this exhaust to propulsion by appropriately mixing it with fan exhaust air.
- the following effects can be obtained in terms of improvement of the flight performance.
- the aircraft propulsion system of the present invention can be preferably applied to an engine portion of aircraft, particularly to an engine portion of large aircraft.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power Engineering (AREA)
- Fuel Cell (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- (1) The second propulsion unit is the electromagnetic driving fan in which the armature coil is disposed on the outer circumference of the fan and the excitation coil is disposed in on the inner peripheral surface of the casing, thus heavy parts such as a core engine and an iron core are not necessary, whereby the configuration thereof can be made simple and the weight thereof can be reduced significantly to be lightweight.
- (2) As a result, the thrust vectoring means for changing a thrust vector, the storage means for storing the second propulsion unit in a wing or folding the unit at a surface of the wing, and the wing driving means for moving the second propulsion unit with respect to a width direction of the wing and a wing chord direction can be realized easily. Accordingly, the optimum thrust and thrust vector for flight conditions can be secured, and the optimum sectional area for the engine in accordance with the flight conditions can also be secured.
- (1) The second propulsion unit is the electromagnetic driving fan which uses the electrical energy as the energy source, thus it doest not discharge exhaust containing harmful substances.
- (2) Since the first propulsion unit comprises the electrical output generating means, the electrical energy is preferably generated and accumulated to enhance an operational ratio of the electromagnetic driving fan, as a result of which the amount of exhaust containing harmful substances is reduced.
- (3) Liquid hydrogen is used as fuel, and the liquid hydrogen brings the armature coil and the excitation coil of the electromagnetic driving fan to a superconductive state, thus there is almost no loss of electrical resistance. As a result, the energy efficiency of the electromagnetic driving fan is improved. Further, the liquid hydrogen exchanges heat with exhaust, the energy of the exhaust is collected, resulting in improvement of the energy efficiency of the entire system.
- (4) Furthermore, the electrical efficiency of the fuel cell is improved due to the fact that vaporized hydrogen gas is provided to the fuel cell and the combustor, and that the fuel cell is disposed between the compressor and the combustor.
- (5) In addition, in the combustor, the temperature of the exhaust is reduced by water vapor which is generated as a result of a combustion reaction, whereby generation of nitrogen oxides is controlled preferably. At the same time, the liquid fuel does not contain carbon compound, and thus does not exhaust carbon dioxide.
- (6) In the electromagnetic driving fan, the armature coil producing electromagnetic force is disposed on the outer circumference of the fan, and then large torque can be produced with small the size of the force, as a result of which the outer diameter of the fan can be enlarged. Accordingly, the bypass ratio can be increased, and the noise level at discharging the exhaust gas is reduced.
- (1) The electromagnetic driving
fan 10 is an electromagnetic driving fan in which the armature coil is disposed on the outer circumference of the fan blade 11 and the excitation coil is disposed in on the inner peripheral surface of the fan casing, thus heavy parts such as a core engine and an iron core are not necessary, whereby the configuration thereof can be made simple and the weight thereof can be reduced significantly to be lightweight. - (2) As a result, the thrust vectoring mechanism for changing a thrust vector, the storage mechanism for storing the second propulsion unit in a wing or folding the unit at a surface of the wing, and the wing driving mechanism for moving the second propulsion unit with respect to a width direction of the wing and a wing chord direction can be realized easily. Accordingly, the optimum thrust and thrust vector for flight conditions can be secured, and the optimum sectional area for the engine in accordance with the flight conditions can also be secured.
- (1) The electromagnetic driving
fan 10 uses the electrical energy as the energy source, thus it doest not discharge exhaust containing harmful substances. - (2) Since the
turbofan engine 1 comprises the electrical output generating means, the electrical energy is preferably generated and accumulated to enhance an operational ratio of the electromagnetic drivingfan 10, as a result of which the amount of exhaust containing harmful substances is reduced. - (3) The electromagnetic driving
fan 10 has the energy collection function and uses liquid hydrogen fuel as fuel for theturbofan engine 1, and the liquid hydrogen brings the armature coil and the excitation coil of the electromagnetic drivingfan 10 to a superconductive state, thus there is almost no loss of electrical resistance. As a result, the energy efficiency of the electromagnetic driving fan is improved. Further, the liquid hydrogen exchanges heat with exhaust, the energy of the exhaust is collected as heat, resulting in improvement of the energy efficiency of the entire system. - (4) Furthermore, the electrical efficiency of the fuel cell is improved due to the fact that vaporized hydrogen gas is provided to the fuel cell and the combustor, and that the fuel cell is disposed between the compressor and the combustor.
- (5) In addition, in the combustor, the temperature of the exhaust is reduced by water vapor which is generated as a result of a combustion reaction, whereby generation of nitrogen oxides is controlled preferably. At the same time, the liquid fuel does not contain carbon compound, and thus does not exhaust carbon dioxide.
- (6) In the electromagnetic driving
fan 10, the armature coil producing electromagnetic force is disposed on the outer circumference of the fan, large torque can be produced with small size of the force, as a result of which the outer diameter of the fan can be enlarged. Accordingly, the bypass ratio can be increased, the noise level at the time of exhaust of exhaust gas is reduced.
Claims (9)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2005016538A JP4092728B2 (en) | 2005-01-25 | 2005-01-25 | Aircraft propulsion system |
JP2005-16538 | 2005-01-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
US20060254255A1 US20060254255A1 (en) | 2006-11-16 |
US7555893B2 true US7555893B2 (en) | 2009-07-07 |
Family
ID=36963070
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/336,828 Expired - Fee Related US7555893B2 (en) | 2005-01-25 | 2006-01-23 | Aircraft propulsion system |
Country Status (2)
Country | Link |
---|---|
US (1) | US7555893B2 (en) |
JP (1) | JP4092728B2 (en) |
Cited By (72)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110227406A1 (en) * | 2010-03-16 | 2011-09-22 | Nguyen Vietson M | Control method for electrical accumulator unit |
US20120275905A1 (en) * | 2011-04-26 | 2012-11-01 | Lockheed Martin Corporation | Lift fan spherical thrust vectoring nozzle |
US8324869B2 (en) | 2010-08-20 | 2012-12-04 | Hamilton Sundstrand Corporation | Method and apparatus for average current control |
US8427108B2 (en) | 2010-08-19 | 2013-04-23 | Hamilton Sundstrand Corporation | Method for controlling an electric accumulator unit |
US8461717B2 (en) | 2010-08-19 | 2013-06-11 | Hamilton Sundstrand Corporation | Active filtering electrical accumulator unit |
US20130234506A1 (en) * | 2010-12-13 | 2013-09-12 | Turbomeca | Method for controlling the generation of electricity applied to an aircraft gas turbine, and device implementing such a method |
US20140008489A1 (en) * | 2011-03-09 | 2014-01-09 | Gunnar Rosenlund | Propulsion System |
US20140367510A1 (en) * | 2013-06-14 | 2014-12-18 | Airbus | Aircraft with electric propulsion means |
US9586690B2 (en) | 2013-03-14 | 2017-03-07 | Rolls-Royce Corporation | Hybrid turbo electric aero-propulsion system control |
US9937803B2 (en) | 2015-05-05 | 2018-04-10 | Rolls-Royce North American Technologies, Inc. | Electric direct drive for aircraft propulsion and lift |
US9963228B2 (en) | 2016-07-01 | 2018-05-08 | Bell Helicopter Textron Inc. | Aircraft with selectively attachable passenger pod assembly |
US10011351B2 (en) * | 2016-07-01 | 2018-07-03 | Bell Helicopter Textron Inc. | Passenger pod assembly transportation system |
US10183746B2 (en) | 2016-07-01 | 2019-01-22 | Bell Helicopter Textron Inc. | Aircraft with independently controllable propulsion assemblies |
US10214285B2 (en) | 2016-07-01 | 2019-02-26 | Bell Helicopter Textron Inc. | Aircraft having autonomous and remote flight control capabilities |
US10220944B2 (en) | 2016-07-01 | 2019-03-05 | Bell Helicopter Textron Inc. | Aircraft having manned and unmanned flight modes |
US10227133B2 (en) | 2016-07-01 | 2019-03-12 | Bell Helicopter Textron Inc. | Transportation method for selectively attachable pod assemblies |
US10232950B2 (en) | 2016-07-01 | 2019-03-19 | Bell Helicopter Textron Inc. | Aircraft having a fault tolerant distributed propulsion system |
US10243355B2 (en) | 2015-06-10 | 2019-03-26 | Rolls-Royce North American Technologies, Inc. | Fault identification and isolation in an electric propulsion system |
US10259590B2 (en) * | 2015-04-16 | 2019-04-16 | Rolls-Royce Plc | Aircraft propulsion system |
US10315761B2 (en) | 2016-07-01 | 2019-06-11 | Bell Helicopter Textron Inc. | Aircraft propulsion assembly |
US10329014B2 (en) | 2017-05-26 | 2019-06-25 | Bell Helicopter Textron Inc. | Aircraft having M-wings |
US10351232B2 (en) | 2017-05-26 | 2019-07-16 | Bell Helicopter Textron Inc. | Rotor assembly having collective pitch control |
US10442522B2 (en) | 2017-05-26 | 2019-10-15 | Bell Textron Inc. | Aircraft with active aerosurfaces |
US10442542B2 (en) | 2015-06-11 | 2019-10-15 | Rolls-Royce North American Technologies, Inc. | Varying quantities of motor poles for noise reduction |
US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
US10501193B2 (en) | 2016-07-01 | 2019-12-10 | Textron Innovations Inc. | Aircraft having a versatile propulsion system |
US10597164B2 (en) | 2016-07-01 | 2020-03-24 | Textron Innovations Inc. | Aircraft having redundant directional control |
US10604249B2 (en) | 2016-07-01 | 2020-03-31 | Textron Innovations Inc. | Man portable aircraft system for rapid in-situ assembly |
US10618647B2 (en) | 2016-07-01 | 2020-04-14 | Textron Innovations Inc. | Mission configurable aircraft having VTOL and biplane orientations |
US10618646B2 (en) | 2017-05-26 | 2020-04-14 | Textron Innovations Inc. | Rotor assembly having a ball joint for thrust vectoring capabilities |
US10625853B2 (en) | 2016-07-01 | 2020-04-21 | Textron Innovations Inc. | Automated configuration of mission specific aircraft |
US10633087B2 (en) | 2016-07-01 | 2020-04-28 | Textron Innovations Inc. | Aircraft having hover stability in inclined flight attitudes |
US10633088B2 (en) | 2016-07-01 | 2020-04-28 | Textron Innovations Inc. | Aerial imaging aircraft having attitude stability during translation |
US10661892B2 (en) | 2017-05-26 | 2020-05-26 | Textron Innovations Inc. | Aircraft having omnidirectional ground maneuver capabilities |
US10717539B2 (en) | 2016-05-05 | 2020-07-21 | Pratt & Whitney Canada Corp. | Hybrid gas-electric turbine engine |
US10737765B2 (en) | 2016-07-01 | 2020-08-11 | Textron Innovations Inc. | Aircraft having single-axis gimbal mounted propulsion systems |
US10737801B2 (en) * | 2016-10-31 | 2020-08-11 | Rolls-Royce Corporation | Fan module with rotatable vane ring power system |
US10737778B2 (en) | 2016-07-01 | 2020-08-11 | Textron Innovations Inc. | Two-axis gimbal mounted propulsion systems for aircraft |
US10774741B2 (en) | 2016-01-26 | 2020-09-15 | General Electric Company | Hybrid propulsion system for a gas turbine engine including a fuel cell |
US10793281B2 (en) | 2017-02-10 | 2020-10-06 | General Electric Company | Propulsion system for an aircraft |
US10822103B2 (en) | 2017-02-10 | 2020-11-03 | General Electric Company | Propulsor assembly for an aircraft |
US10870487B2 (en) | 2016-07-01 | 2020-12-22 | Bell Textron Inc. | Logistics support aircraft having a minimal drag configuration |
US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
US20210078702A1 (en) * | 2019-09-16 | 2021-03-18 | Airbus Operations Sas | Aircraft having support stays for wings in which hydrogen pipes or electrical conductors are arranged |
US10981661B2 (en) | 2016-07-01 | 2021-04-20 | Textron Innovations Inc. | Aircraft having multiple independent yaw authority mechanisms |
US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
US11027837B2 (en) | 2016-07-01 | 2021-06-08 | Textron Innovations Inc. | Aircraft having thrust to weight dependent transitions |
US11084579B2 (en) | 2016-07-01 | 2021-08-10 | Textron Innovations Inc. | Convertible biplane aircraft for capturing drones |
US11104446B2 (en) | 2016-07-01 | 2021-08-31 | Textron Innovations Inc. | Line replaceable propulsion assemblies for aircraft |
US11124289B2 (en) | 2016-07-01 | 2021-09-21 | Textron Innovations Inc. | Prioritizing use of flight attitude controls of aircraft |
US11142311B2 (en) | 2016-07-01 | 2021-10-12 | Textron Innovations Inc. | VTOL aircraft for external load operations |
US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
US11312491B2 (en) | 2019-10-23 | 2022-04-26 | Textron Innovations Inc. | Convertible biplane aircraft for autonomous cargo delivery |
US11312502B2 (en) | 2015-01-23 | 2022-04-26 | General Electric Company | Gas-electric propulsion system for an aircraft |
US20220127969A1 (en) * | 2020-10-26 | 2022-04-28 | Francis O'Neill | Gas turbine propulsion system |
US11319064B1 (en) | 2020-11-04 | 2022-05-03 | Textron Innovations Inc. | Autonomous payload deployment aircraft |
US11465763B2 (en) * | 2017-03-19 | 2022-10-11 | Zunum Aero, Inc. | Hybrid-electric aircraft, and methods, apparatus and systems for facilitating same |
US11530035B2 (en) | 2020-08-27 | 2022-12-20 | Textron Innovations Inc. | VTOL aircraft having multiple wing planforms |
US11608173B2 (en) | 2016-07-01 | 2023-03-21 | Textron Innovations Inc. | Aerial delivery systems using unmanned aircraft |
US11630467B2 (en) | 2020-12-23 | 2023-04-18 | Textron Innovations Inc. | VTOL aircraft having multifocal landing sensors |
US11643207B1 (en) | 2021-12-07 | 2023-05-09 | Textron Innovations Inc. | Aircraft for transporting and deploying UAVs |
US11673662B1 (en) | 2022-01-05 | 2023-06-13 | Textron Innovations Inc. | Telescoping tail assemblies for use on aircraft |
US11773782B2 (en) | 2020-12-23 | 2023-10-03 | Rtx Corporation | Gas turbine engines having cryogenic fuel systems |
US11820526B2 (en) | 2020-02-26 | 2023-11-21 | Honda Motor Co., Ltd. | Power supply apparatus for a flying body including a combustion gas and intake air heat exchanger |
US11873768B1 (en) | 2022-09-16 | 2024-01-16 | General Electric Company | Hydrogen fuel system for a gas turbine engine |
US11898495B1 (en) | 2022-09-16 | 2024-02-13 | General Electric Company | Hydrogen fuel system for a gas turbine engine |
US11905884B1 (en) | 2022-09-16 | 2024-02-20 | General Electric Company | Hydrogen fuel system for a gas turbine engine |
US11912423B2 (en) | 2022-04-06 | 2024-02-27 | Rtx Corporation | Hydrogen steam and inter-cooled turbine engine |
US11932387B2 (en) | 2021-12-02 | 2024-03-19 | Textron Innovations Inc. | Adaptive transition systems for VTOL aircraft |
US11987377B2 (en) | 2022-07-08 | 2024-05-21 | Rtx Corporation | Turbo expanders for turbine engines having hydrogen fuel systems |
US12044176B2 (en) | 2021-07-09 | 2024-07-23 | Rtx Corporation | Turbine engines having hydrogen fuel systems |
US12084200B2 (en) | 2021-11-03 | 2024-09-10 | Textron Innovations Inc. | Ground state determination systems for aircraft |
Families Citing this family (67)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20060272863A1 (en) * | 2005-06-02 | 2006-12-07 | Brad Donahue | Electric vehicle with regeneration |
US7808118B2 (en) * | 2005-07-14 | 2010-10-05 | Berkson Bruce R | Method for creating energy sources for a vehicle drive system |
US7622817B2 (en) * | 2006-12-13 | 2009-11-24 | General Electric Company | High-speed high-pole count generators |
US8291716B2 (en) * | 2008-10-08 | 2012-10-23 | The Invention Science Fund I Llc | Hybrid propulsive engine including at least one independently rotatable turbine stator |
US8857191B2 (en) * | 2008-10-08 | 2014-10-14 | The Invention Science Fund I, Llc | Hybrid propulsive engine including at least one independently rotatable propeller/fan |
US20100083632A1 (en) * | 2008-10-08 | 2010-04-08 | Searete Llc, A Limited Liability Corporation Of The State Of Delaware | Hybrid propulsive engine including at least one independently rotatable compressor rotor |
US20100126178A1 (en) * | 2008-10-08 | 2010-05-27 | Searete Llc, A Limited Liability Corporation Of The State Of Delaware | Hybrid propulsive engine including at least one independently rotatable turbine stator |
FR2941492B1 (en) * | 2009-01-23 | 2011-09-09 | Snecma | POWER TURBINE TURBINE ENGINE COMPRISING AN ELECTRONIC POWER GENERATOR CENTERED ON THE AXIS OF TURBOMACHINE |
RU2466908C2 (en) * | 2010-05-18 | 2012-11-20 | Николай Иванович Максимов | Integrated technology of operation and production "maxinio" transport facilities: vtol electric aircraft (versions), electric aircraft units and methods of employment electric aircraft and its parts |
DE102011105880B4 (en) | 2011-06-14 | 2014-05-08 | Eads Deutschland Gmbh | Electric drive device for an aircraft |
GB201116759D0 (en) * | 2011-09-29 | 2011-11-09 | Rolls Royce Plc | A superconducting electrical system |
US8220570B1 (en) | 2011-12-14 | 2012-07-17 | Knickerbocker Cecil G | Electric vehicle with energy producing system and method of using the same |
US8579054B2 (en) | 2011-12-14 | 2013-11-12 | Cecil G. Knickerbocker | Electric vehicle with energy producing system and method of using the same |
US8464511B1 (en) * | 2012-01-06 | 2013-06-18 | Hamilton Sundstrand Corporation | Magnetically coupled contra-rotating propulsion stages |
FR2994707B1 (en) * | 2012-08-21 | 2018-04-06 | Snecma | HYBRID TURBOMACHINE WITH CONTRAROTATIVE PROPELLERS |
RU2534676C1 (en) * | 2013-05-27 | 2014-12-10 | Дмитрий Сергеевич Дуров | Cryogenic turbo-electric stol aircraft |
CN105339597B (en) * | 2013-06-07 | 2017-03-22 | 通用电气航空系统有限责任公司 | Turbofan engine with generator |
US10071801B2 (en) | 2013-08-13 | 2018-09-11 | The United States Of America As Represented By The Administrator Of Nasa | Tri-rotor aircraft capable of vertical takeoff and landing and transitioning to forward flight |
US9475579B2 (en) | 2013-08-13 | 2016-10-25 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Vertical take-off and landing vehicle with increased cruise efficiency |
DE102013013849A1 (en) * | 2013-08-20 | 2015-03-12 | Astrium Gmbh | Landing system for an aircraft or spacecraft |
EP2878795B8 (en) * | 2013-11-27 | 2016-10-12 | Airbus Operations GmbH | Engine for propelling an aircraft and aircraft having at least one engine and at least one hydrogen tank |
GB201320988D0 (en) * | 2013-11-28 | 2014-01-15 | Rolls Royce Plc | An aircraft |
US9637243B2 (en) * | 2013-12-23 | 2017-05-02 | Safe Flight Instrument Corporation | Aircraft lift transducer |
RU2554043C1 (en) * | 2014-02-13 | 2015-06-20 | Дмитрий Сергеевич Дуров | Hybrid short takeoff and landing electric aircraft |
JP6400920B2 (en) * | 2014-02-27 | 2018-10-03 | 学校法人日本大学 | Motor jet engine |
EP2942226A1 (en) * | 2014-05-06 | 2015-11-11 | Airbus Operations GmbH | Aircraft battery exhaust system |
WO2015191017A1 (en) * | 2014-06-13 | 2015-12-17 | Oran Bülent | Propeller with super conductive electrical motor for air vehicles |
RU2558168C1 (en) * | 2014-07-01 | 2015-07-27 | Дмитрий Сергеевич Дуров | Hybrid short takeoff and landing electric aircraft |
ES2644782T3 (en) | 2014-09-17 | 2017-11-30 | Airbus Operations, S.L. | Aircraft hybrid engine |
DE102014224637B4 (en) * | 2014-12-02 | 2022-12-29 | Georgi Atanasov | Hybrid electric propulsion system for an aircraft |
JP6437347B2 (en) * | 2015-02-27 | 2018-12-12 | 三菱重工業株式会社 | Thrust generator and aircraft |
US10370100B2 (en) | 2015-03-24 | 2019-08-06 | United States Of America As Represented By The Administrator Of Nasa | Aerodynamically actuated thrust vectoring devices |
DE102015209672A1 (en) * | 2015-05-27 | 2016-12-01 | Siemens Aktiengesellschaft | Airplane and method of operating a hydrofoil |
DE102015215130A1 (en) * | 2015-08-07 | 2017-02-09 | Siemens Aktiengesellschaft | Drive system and method for driving a propulsion means of a vehicle |
US9731608B1 (en) | 2015-11-03 | 2017-08-15 | Cecil Knickerbocker | Electric vehicle with energy producing system and method of using the same |
KR101685853B1 (en) * | 2015-11-30 | 2016-12-20 | 한국항공우주연구원 | Dual fuel internal combustion engine impelling apparatus |
KR101757442B1 (en) * | 2016-02-22 | 2017-07-12 | 하이리움산업(주) | Fuel Cell Power-pack for Multi-copter |
US9764848B1 (en) * | 2016-03-07 | 2017-09-19 | General Electric Company | Propulsion system for an aircraft |
US10180080B2 (en) * | 2016-03-09 | 2019-01-15 | Rolls-Royce North American Technologies, Inc. | Electromagnetic propeller brake |
US10518863B2 (en) * | 2016-04-22 | 2019-12-31 | Rolls-Royce Plc | Aircraft electrical network |
GB2554063B (en) * | 2016-09-01 | 2022-03-30 | Lynley Ashley Adrian | Dual servo differential turbofan engine |
DE102016219680A1 (en) * | 2016-10-11 | 2018-04-12 | Siemens Aktiengesellschaft | Drive system for a vehicle with internal combustion engine and fuel tank |
GB2558228B (en) * | 2016-12-22 | 2020-05-20 | Rolls Royce Plc | Aircraft electrically-assisted propulsion control system |
GB201708297D0 (en) * | 2017-05-24 | 2017-07-05 | Rolls Royce Plc | Preventing electrical breakdown |
DE102017223803A1 (en) * | 2017-12-27 | 2019-06-27 | Siemens Aktiengesellschaft | Electric drive system, vehicle and method for driving a vehicle |
RO133664B1 (en) | 2018-04-17 | 2024-07-30 | Răzvan Sabie | Aircraft with vertical take-off and landing |
GB201807769D0 (en) * | 2018-05-14 | 2018-06-27 | Rolls Royce Plc | Electric ducted fan |
GB201807770D0 (en) * | 2018-05-14 | 2018-06-27 | Rolls Royce Plc | Electric ducted fan |
US10738694B1 (en) | 2018-08-23 | 2020-08-11 | United Technologies Corporation | Turbofan with motorized rotating inlet guide vane |
CN110963052A (en) * | 2018-09-30 | 2020-04-07 | 中国航发商用航空发动机有限责任公司 | Distributed propulsion system, aircraft and propulsion method |
JP7191624B2 (en) * | 2018-10-03 | 2022-12-19 | 三菱重工航空エンジン株式会社 | internal combustion engine |
GB2587560A (en) * | 2018-10-15 | 2021-03-31 | Gkn Aerospace Services Ltd | Apparatus |
GB2587556B (en) * | 2018-10-15 | 2021-09-15 | Gkn Aerospace Services Ltd | Aircraft propulsion incorporating a cryogen |
GB2587559B (en) * | 2018-10-15 | 2022-04-13 | Gkn Aerospace Services Ltd | Apparatus |
GB2578288B (en) * | 2018-10-15 | 2022-04-13 | Gkn Aerospace Services Ltd | Apparatus |
CN111216901A (en) * | 2018-11-26 | 2020-06-02 | 本田技研工业株式会社 | Power supply device and flying object |
US11267335B1 (en) | 2018-11-27 | 2022-03-08 | Cecil Knickerbocker | Electric vehicle with power controller for distributing and enhancing energy from a generator |
JP7297574B2 (en) * | 2019-07-12 | 2023-06-26 | 三菱重工業株式会社 | GAS TURBINE SYSTEM AND MOVING OBJECT WITH THE SAME |
JP7293014B2 (en) * | 2019-07-12 | 2023-06-19 | 三菱重工業株式会社 | GAS TURBINE SYSTEM AND MOVING OBJECT WITH THE SAME |
US11912422B2 (en) * | 2019-08-26 | 2024-02-27 | Hamilton Sundstrand Corporation | Hybrid electric aircraft and powerplant arrangements |
JP7519791B2 (en) * | 2020-03-13 | 2024-07-22 | 本田技研工業株式会社 | Power supply unit and flying object |
US11002146B1 (en) | 2020-10-26 | 2021-05-11 | Antheon Research, Inc. | Power generation system |
WO2022098677A1 (en) * | 2020-11-03 | 2022-05-12 | Clear Ascent Corp. | Systems and methods for propulsion |
CA3214218A1 (en) * | 2021-04-02 | 2022-10-06 | Zeroavia Ltd. | Hybrid hydrogen-electric and hydrogen turbine engine and system |
GB202114829D0 (en) * | 2021-10-18 | 2021-12-01 | Rolls Royce Plc | Aircraft propulsion system |
EP4173956A1 (en) * | 2021-10-29 | 2023-05-03 | Airbus S.A.S. | Hybrid propulsion system for propelling an aircraft, method of operating same, and hybrid aircraft |
WO2024018988A1 (en) * | 2022-07-21 | 2024-01-25 | 株式会社Ihi | Aircraft hybrid motive power source system and method for controlling same |
Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2939648A (en) * | 1954-03-27 | 1960-06-07 | Paul O Tobeler | Rotating jet aircraft with lifting disc wing and centrifuging tanks |
US3408517A (en) * | 1966-02-23 | 1968-10-29 | Gen Electric | Multiple circuit winding patterns for polyphase dynamoelectric machines |
US3437290A (en) * | 1967-04-24 | 1969-04-08 | Francis A Norman | Vertical lift aircraft |
US4698563A (en) * | 1986-03-04 | 1987-10-06 | Itsuki Ban | Semiconductor electric motor having a rotary transformer to excite a rotor |
US5333444A (en) * | 1993-02-11 | 1994-08-02 | The United States Of America As Represented By The Secretary Of The Navy | Superconducting electromagnetic thruster |
US5469816A (en) * | 1993-09-02 | 1995-11-28 | Nippondenso Co., Ltd. | Control mechanism for an electric generator motor in an internal combustion engine |
US5842667A (en) * | 1994-03-31 | 1998-12-01 | Jones; Tommy Lee | Vertical takeoff and landing mass transit system and method |
JPH11200888A (en) | 1998-01-19 | 1999-07-27 | Mitsubishi Heavy Ind Ltd | Fuel cell type turbine engine |
US6111390A (en) * | 1998-01-20 | 2000-08-29 | Kokusan Kenki Co., Ltd. | Magneto-equipped power device |
US6296957B1 (en) * | 1998-05-15 | 2001-10-02 | Xcellsis Gmbh | Energy supply unit on board an aircraft |
US20030080242A1 (en) * | 2001-10-31 | 2003-05-01 | Hideharu Kawai | Vertical takeoff and landing aircraft |
US20040069901A1 (en) * | 2000-05-15 | 2004-04-15 | Nunnally William C. | Aircraft and hybrid with magnetic airfoil suspension and drive |
US20050001582A1 (en) * | 2003-04-10 | 2005-01-06 | Hitachi, Ltd. | Motor control device |
US20050162030A1 (en) * | 2004-01-27 | 2005-07-28 | Shah Manoj R. | Brushless exciter with electromagnetically decoupled dual excitation systems for starter-generator applications |
US20050181246A1 (en) * | 2002-11-07 | 2005-08-18 | Nissan Motor Co., Ltd. | Fuel cell system and related method |
US20050206268A1 (en) * | 2000-06-14 | 2005-09-22 | Walter Richard T | Motor armature having distributed windings for reducing arcing |
US7032861B2 (en) * | 2002-01-07 | 2006-04-25 | Sanders Jr John K | Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors |
-
2005
- 2005-01-25 JP JP2005016538A patent/JP4092728B2/en not_active Expired - Fee Related
-
2006
- 2006-01-23 US US11/336,828 patent/US7555893B2/en not_active Expired - Fee Related
Patent Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2939648A (en) * | 1954-03-27 | 1960-06-07 | Paul O Tobeler | Rotating jet aircraft with lifting disc wing and centrifuging tanks |
US3408517A (en) * | 1966-02-23 | 1968-10-29 | Gen Electric | Multiple circuit winding patterns for polyphase dynamoelectric machines |
US3437290A (en) * | 1967-04-24 | 1969-04-08 | Francis A Norman | Vertical lift aircraft |
US4698563A (en) * | 1986-03-04 | 1987-10-06 | Itsuki Ban | Semiconductor electric motor having a rotary transformer to excite a rotor |
US5333444A (en) * | 1993-02-11 | 1994-08-02 | The United States Of America As Represented By The Secretary Of The Navy | Superconducting electromagnetic thruster |
US5469816A (en) * | 1993-09-02 | 1995-11-28 | Nippondenso Co., Ltd. | Control mechanism for an electric generator motor in an internal combustion engine |
US5842667A (en) * | 1994-03-31 | 1998-12-01 | Jones; Tommy Lee | Vertical takeoff and landing mass transit system and method |
JPH11200888A (en) | 1998-01-19 | 1999-07-27 | Mitsubishi Heavy Ind Ltd | Fuel cell type turbine engine |
US6111390A (en) * | 1998-01-20 | 2000-08-29 | Kokusan Kenki Co., Ltd. | Magneto-equipped power device |
US6296957B1 (en) * | 1998-05-15 | 2001-10-02 | Xcellsis Gmbh | Energy supply unit on board an aircraft |
US20040069901A1 (en) * | 2000-05-15 | 2004-04-15 | Nunnally William C. | Aircraft and hybrid with magnetic airfoil suspension and drive |
US20050206268A1 (en) * | 2000-06-14 | 2005-09-22 | Walter Richard T | Motor armature having distributed windings for reducing arcing |
US20030080242A1 (en) * | 2001-10-31 | 2003-05-01 | Hideharu Kawai | Vertical takeoff and landing aircraft |
US7032861B2 (en) * | 2002-01-07 | 2006-04-25 | Sanders Jr John K | Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors |
US20050181246A1 (en) * | 2002-11-07 | 2005-08-18 | Nissan Motor Co., Ltd. | Fuel cell system and related method |
US20050001582A1 (en) * | 2003-04-10 | 2005-01-06 | Hitachi, Ltd. | Motor control device |
US20050162030A1 (en) * | 2004-01-27 | 2005-07-28 | Shah Manoj R. | Brushless exciter with electromagnetically decoupled dual excitation systems for starter-generator applications |
Cited By (99)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110227406A1 (en) * | 2010-03-16 | 2011-09-22 | Nguyen Vietson M | Control method for electrical accumulator unit |
US8427108B2 (en) | 2010-08-19 | 2013-04-23 | Hamilton Sundstrand Corporation | Method for controlling an electric accumulator unit |
US8461717B2 (en) | 2010-08-19 | 2013-06-11 | Hamilton Sundstrand Corporation | Active filtering electrical accumulator unit |
US8324869B2 (en) | 2010-08-20 | 2012-12-04 | Hamilton Sundstrand Corporation | Method and apparatus for average current control |
US20130234506A1 (en) * | 2010-12-13 | 2013-09-12 | Turbomeca | Method for controlling the generation of electricity applied to an aircraft gas turbine, and device implementing such a method |
US8866318B2 (en) * | 2010-12-13 | 2014-10-21 | Turbomeca | Method for controlling the generation of electricity applied to an aircraft gas turbine, and device implementing such a method |
US9067687B2 (en) * | 2011-03-09 | 2015-06-30 | Gunnar Rosenlund | Propulsion system with movably mounted engines |
US20140008489A1 (en) * | 2011-03-09 | 2014-01-09 | Gunnar Rosenlund | Propulsion System |
US8910464B2 (en) * | 2011-04-26 | 2014-12-16 | Lockheed Martin Corporation | Lift fan spherical thrust vectoring nozzle |
US20120275905A1 (en) * | 2011-04-26 | 2012-11-01 | Lockheed Martin Corporation | Lift fan spherical thrust vectoring nozzle |
US9586690B2 (en) | 2013-03-14 | 2017-03-07 | Rolls-Royce Corporation | Hybrid turbo electric aero-propulsion system control |
US20140367510A1 (en) * | 2013-06-14 | 2014-12-18 | Airbus | Aircraft with electric propulsion means |
US9950801B2 (en) * | 2013-06-14 | 2018-04-24 | Airbus Sas | Aircraft with electric propulsion means |
US11673678B2 (en) | 2015-01-23 | 2023-06-13 | General Electric Company | Gas-electric propulsion system for an aircraft |
US11312502B2 (en) | 2015-01-23 | 2022-04-26 | General Electric Company | Gas-electric propulsion system for an aircraft |
US10259590B2 (en) * | 2015-04-16 | 2019-04-16 | Rolls-Royce Plc | Aircraft propulsion system |
US9937803B2 (en) | 2015-05-05 | 2018-04-10 | Rolls-Royce North American Technologies, Inc. | Electric direct drive for aircraft propulsion and lift |
US10427527B2 (en) | 2015-05-05 | 2019-10-01 | Rolls-Royce Corporation | Electric direct drive for aircraft propulsion and lift |
US10243355B2 (en) | 2015-06-10 | 2019-03-26 | Rolls-Royce North American Technologies, Inc. | Fault identification and isolation in an electric propulsion system |
US10988035B2 (en) | 2015-06-11 | 2021-04-27 | Rolls-Royce Corporation | Varying quantities of motor poles for noise reduction |
US10442542B2 (en) | 2015-06-11 | 2019-10-15 | Rolls-Royce North American Technologies, Inc. | Varying quantities of motor poles for noise reduction |
US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
US10774741B2 (en) | 2016-01-26 | 2020-09-15 | General Electric Company | Hybrid propulsion system for a gas turbine engine including a fuel cell |
US10717539B2 (en) | 2016-05-05 | 2020-07-21 | Pratt & Whitney Canada Corp. | Hybrid gas-electric turbine engine |
US10752350B2 (en) | 2016-07-01 | 2020-08-25 | Textron Innovations Inc. | Autonomous package delivery aircraft |
US11091257B2 (en) | 2016-07-01 | 2021-08-17 | Textron Innovations Inc. | Autonomous package delivery aircraft |
US10343773B1 (en) | 2016-07-01 | 2019-07-09 | Bell Helicopter Textron Inc. | Aircraft having pod assembly jettison capabilities |
US11767112B2 (en) | 2016-07-01 | 2023-09-26 | Textron Innovations Inc. | Aircraft having a magnetically couplable payload module |
US10322799B2 (en) * | 2016-07-01 | 2019-06-18 | Bell Helicopter Textron Inc. | Transportation services for pod assemblies |
US9963228B2 (en) | 2016-07-01 | 2018-05-08 | Bell Helicopter Textron Inc. | Aircraft with selectively attachable passenger pod assembly |
US10315761B2 (en) | 2016-07-01 | 2019-06-11 | Bell Helicopter Textron Inc. | Aircraft propulsion assembly |
US10457390B2 (en) | 2016-07-01 | 2019-10-29 | Bell Textron Inc. | Aircraft with thrust vectoring propulsion assemblies |
US10232950B2 (en) | 2016-07-01 | 2019-03-19 | Bell Helicopter Textron Inc. | Aircraft having a fault tolerant distributed propulsion system |
US10501193B2 (en) | 2016-07-01 | 2019-12-10 | Textron Innovations Inc. | Aircraft having a versatile propulsion system |
US10583921B1 (en) | 2016-07-01 | 2020-03-10 | Textron Innovations Inc. | Aircraft generating thrust in multiple directions |
US10597164B2 (en) | 2016-07-01 | 2020-03-24 | Textron Innovations Inc. | Aircraft having redundant directional control |
US10604249B2 (en) | 2016-07-01 | 2020-03-31 | Textron Innovations Inc. | Man portable aircraft system for rapid in-situ assembly |
US10611477B1 (en) | 2016-07-01 | 2020-04-07 | Textron Innovations Inc. | Closed wing aircraft having a distributed propulsion system |
US10618647B2 (en) | 2016-07-01 | 2020-04-14 | Textron Innovations Inc. | Mission configurable aircraft having VTOL and biplane orientations |
US11649061B2 (en) | 2016-07-01 | 2023-05-16 | Textron Innovations Inc. | Aircraft having multiple independent yaw authority mechanisms |
US10625853B2 (en) | 2016-07-01 | 2020-04-21 | Textron Innovations Inc. | Automated configuration of mission specific aircraft |
US10633087B2 (en) | 2016-07-01 | 2020-04-28 | Textron Innovations Inc. | Aircraft having hover stability in inclined flight attitudes |
US10633088B2 (en) | 2016-07-01 | 2020-04-28 | Textron Innovations Inc. | Aerial imaging aircraft having attitude stability during translation |
US11608173B2 (en) | 2016-07-01 | 2023-03-21 | Textron Innovations Inc. | Aerial delivery systems using unmanned aircraft |
US10227133B2 (en) | 2016-07-01 | 2019-03-12 | Bell Helicopter Textron Inc. | Transportation method for selectively attachable pod assemblies |
US10737765B2 (en) | 2016-07-01 | 2020-08-11 | Textron Innovations Inc. | Aircraft having single-axis gimbal mounted propulsion systems |
US11603194B2 (en) | 2016-07-01 | 2023-03-14 | Textron Innovations Inc. | Aircraft having a high efficiency forward flight mode |
US10737778B2 (en) | 2016-07-01 | 2020-08-11 | Textron Innovations Inc. | Two-axis gimbal mounted propulsion systems for aircraft |
US10220944B2 (en) | 2016-07-01 | 2019-03-05 | Bell Helicopter Textron Inc. | Aircraft having manned and unmanned flight modes |
US10214285B2 (en) | 2016-07-01 | 2019-02-26 | Bell Helicopter Textron Inc. | Aircraft having autonomous and remote flight control capabilities |
US11383823B2 (en) | 2016-07-01 | 2022-07-12 | Textron Innovations Inc. | Single-axis gimbal mounted propulsion systems for aircraft |
US11312487B2 (en) | 2016-07-01 | 2022-04-26 | Textron Innovations Inc. | Aircraft generating thrust in multiple directions |
US10870487B2 (en) | 2016-07-01 | 2020-12-22 | Bell Textron Inc. | Logistics support aircraft having a minimal drag configuration |
US10183746B2 (en) | 2016-07-01 | 2019-01-22 | Bell Helicopter Textron Inc. | Aircraft with independently controllable propulsion assemblies |
US10913541B2 (en) | 2016-07-01 | 2021-02-09 | Textron Innovations Inc. | Aircraft having redundant directional control |
US10011351B2 (en) * | 2016-07-01 | 2018-07-03 | Bell Helicopter Textron Inc. | Passenger pod assembly transportation system |
US10981661B2 (en) | 2016-07-01 | 2021-04-20 | Textron Innovations Inc. | Aircraft having multiple independent yaw authority mechanisms |
US20180281943A1 (en) * | 2016-07-01 | 2018-10-04 | Bell Helicopter Textron Inc. | Transportation Services for Pod Assemblies |
US11142311B2 (en) | 2016-07-01 | 2021-10-12 | Textron Innovations Inc. | VTOL aircraft for external load operations |
US11027837B2 (en) | 2016-07-01 | 2021-06-08 | Textron Innovations Inc. | Aircraft having thrust to weight dependent transitions |
US11084579B2 (en) | 2016-07-01 | 2021-08-10 | Textron Innovations Inc. | Convertible biplane aircraft for capturing drones |
US11126203B2 (en) | 2016-07-01 | 2021-09-21 | Textron Innovations Inc. | Aerial imaging aircraft having attitude stability |
US11104446B2 (en) | 2016-07-01 | 2021-08-31 | Textron Innovations Inc. | Line replaceable propulsion assemblies for aircraft |
US11124289B2 (en) | 2016-07-01 | 2021-09-21 | Textron Innovations Inc. | Prioritizing use of flight attitude controls of aircraft |
US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
US10737801B2 (en) * | 2016-10-31 | 2020-08-11 | Rolls-Royce Corporation | Fan module with rotatable vane ring power system |
US10822103B2 (en) | 2017-02-10 | 2020-11-03 | General Electric Company | Propulsor assembly for an aircraft |
US10793281B2 (en) | 2017-02-10 | 2020-10-06 | General Electric Company | Propulsion system for an aircraft |
US11465763B2 (en) * | 2017-03-19 | 2022-10-11 | Zunum Aero, Inc. | Hybrid-electric aircraft, and methods, apparatus and systems for facilitating same |
US20230182908A1 (en) * | 2017-03-19 | 2023-06-15 | Zunum Aero, Inc. | Hybrid-electric aircraft, and methods, apparatus and systems for facilitating same |
US10351232B2 (en) | 2017-05-26 | 2019-07-16 | Bell Helicopter Textron Inc. | Rotor assembly having collective pitch control |
US10442522B2 (en) | 2017-05-26 | 2019-10-15 | Bell Textron Inc. | Aircraft with active aerosurfaces |
US11459099B2 (en) | 2017-05-26 | 2022-10-04 | Textron Innovations Inc. | M-wing aircraft having VTOL and biplane orientations |
US11505302B2 (en) | 2017-05-26 | 2022-11-22 | Textron Innovations Inc. | Rotor assembly having collective pitch control |
US10618646B2 (en) | 2017-05-26 | 2020-04-14 | Textron Innovations Inc. | Rotor assembly having a ball joint for thrust vectoring capabilities |
US10661892B2 (en) | 2017-05-26 | 2020-05-26 | Textron Innovations Inc. | Aircraft having omnidirectional ground maneuver capabilities |
US10329014B2 (en) | 2017-05-26 | 2019-06-25 | Bell Helicopter Textron Inc. | Aircraft having M-wings |
US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
US20210078702A1 (en) * | 2019-09-16 | 2021-03-18 | Airbus Operations Sas | Aircraft having support stays for wings in which hydrogen pipes or electrical conductors are arranged |
US11661181B2 (en) * | 2019-09-16 | 2023-05-30 | Airbus Operations Sas | Aircraft having support stays for wings in which hydrogen pipes or electrical conductors are arranged |
US11312491B2 (en) | 2019-10-23 | 2022-04-26 | Textron Innovations Inc. | Convertible biplane aircraft for autonomous cargo delivery |
US11820526B2 (en) | 2020-02-26 | 2023-11-21 | Honda Motor Co., Ltd. | Power supply apparatus for a flying body including a combustion gas and intake air heat exchanger |
US11530035B2 (en) | 2020-08-27 | 2022-12-20 | Textron Innovations Inc. | VTOL aircraft having multiple wing planforms |
US11530617B2 (en) * | 2020-10-26 | 2022-12-20 | Antheon Research, Inc. | Gas turbine propulsion system |
US20220127969A1 (en) * | 2020-10-26 | 2022-04-28 | Francis O'Neill | Gas turbine propulsion system |
US11319064B1 (en) | 2020-11-04 | 2022-05-03 | Textron Innovations Inc. | Autonomous payload deployment aircraft |
US11630467B2 (en) | 2020-12-23 | 2023-04-18 | Textron Innovations Inc. | VTOL aircraft having multifocal landing sensors |
US11773782B2 (en) | 2020-12-23 | 2023-10-03 | Rtx Corporation | Gas turbine engines having cryogenic fuel systems |
US12044176B2 (en) | 2021-07-09 | 2024-07-23 | Rtx Corporation | Turbine engines having hydrogen fuel systems |
US12084200B2 (en) | 2021-11-03 | 2024-09-10 | Textron Innovations Inc. | Ground state determination systems for aircraft |
US11932387B2 (en) | 2021-12-02 | 2024-03-19 | Textron Innovations Inc. | Adaptive transition systems for VTOL aircraft |
US11643207B1 (en) | 2021-12-07 | 2023-05-09 | Textron Innovations Inc. | Aircraft for transporting and deploying UAVs |
US11673662B1 (en) | 2022-01-05 | 2023-06-13 | Textron Innovations Inc. | Telescoping tail assemblies for use on aircraft |
US11912423B2 (en) | 2022-04-06 | 2024-02-27 | Rtx Corporation | Hydrogen steam and inter-cooled turbine engine |
US11987377B2 (en) | 2022-07-08 | 2024-05-21 | Rtx Corporation | Turbo expanders for turbine engines having hydrogen fuel systems |
US11873768B1 (en) | 2022-09-16 | 2024-01-16 | General Electric Company | Hydrogen fuel system for a gas turbine engine |
US11898495B1 (en) | 2022-09-16 | 2024-02-13 | General Electric Company | Hydrogen fuel system for a gas turbine engine |
US11905884B1 (en) | 2022-09-16 | 2024-02-20 | General Electric Company | Hydrogen fuel system for a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
JP2006205755A (en) | 2006-08-10 |
US20060254255A1 (en) | 2006-11-16 |
JP4092728B2 (en) | 2008-05-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7555893B2 (en) | Aircraft propulsion system | |
EP3623603B1 (en) | Hybrid expander cycle with turbo-generator and cooled power electronics | |
US20240067348A1 (en) | Hybrid Electric Hydrogen Fuel Cell Engine | |
US12060830B2 (en) | Exhaust-gas treatment device for an aircraft engine | |
US11092031B2 (en) | Drive system for an aircraft | |
US20230272761A1 (en) | Superconducting ultra power efficient radial fan augmented nano-aero drive (superfan) | |
US7423405B2 (en) | Electromagnetic rotating machine | |
Radebaugh | Cryocoolers for aircraft superconducting generators and motors | |
KR20230004782A (en) | motor drive system | |
EP4279722A1 (en) | Hydrogen fueled turbine engine pinch point water separator | |
CN101694189A (en) | Super-conducting electromagnetic pump circulating system of liquid rocket engine | |
US20240287931A1 (en) | Hybrid electric hydrogen engine for aircraft | |
JPH08189457A (en) | Solar thermal power generation system | |
EP4336030A1 (en) | A thermal management system for an aircraft | |
WO2023041928A1 (en) | Integrated fan and battery propulsion system | |
de Bock et al. | Progress Toward Climate-Friendly Aviation in the ARPA-E ASCEND and REEACH Programs | |
Bai et al. | Cryogenic turbo-electric hybrid propulsion system with liquid hydrogen cooling for a regional aircraft | |
Duan | An RDF Jet Engine for 20-Passenger Electric Plane and for VTOL of Commercial Aircraft | |
US20240254898A1 (en) | Power electronics waste heat recovery in recuperation cycle | |
CN116374179B (en) | Series hybrid electric propulsion system | |
Okai et al. | Electromagnetic-Driving Fan for Aircraft-Propulsion Application | |
Kojima et al. | Investigation of Weight and Flight-Path Constraints on Liquid Hydrogen Fueled SOFC/GT Hybrid Propulsion System | |
Palethorpe et al. | Very long endurance propulsion systems | |
WO2024009097A1 (en) | Aircraft propulsion system and method | |
CN117644979A (en) | Double-motor hybrid aeroengine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: NIHON UNIVERSITY, JAPAN Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:OKAI, KEIICHI;TAGASHIRA, TAKESHI;YANAGI, RYOJI;AND OTHERS;REEL/FRAME:017500/0461;SIGNING DATES FROM 20051215 TO 20051219 Owner name: AIRCRAFT AEROSPACE EXPLORATION AGENCY, JAPAN Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:OKAI, KEIICHI;TAGASHIRA, TAKESHI;YANAGI, RYOJI;AND OTHERS;REEL/FRAME:017500/0461;SIGNING DATES FROM 20051215 TO 20051219 |
|
AS | Assignment |
Owner name: JAPAN AIRCRAFT AEROSPACE EXPLORATION AGENCY, JAPAN Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE FIRST ASSIGNEE'S NAME PREVIOUSLY RECORDED ON REEL 017500 FRAME 0461;ASSIGNORS:OKAI, KEIICHI;TAGASHIRA, TAKESHI;YANAGI, RYOJI;AND OTHERS;REEL/FRAME:017631/0249 Effective date: 20051219 |
|
AS | Assignment |
Owner name: JAPAN AEROSPACE EXPLORATION AGENCY, JAPAN Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE 4TH INVENTOR'S EXECUTION DATE AND 1ST ASSIGNEE'S NAME AND TO ADD THE 2ND ASSIGNEE'S INFORMATION PREVIOUSLY RECORDED ON REEL 017631 FRAME 0249;ASSIGNORS:OKAI, KEIICHI;TAGASHIRA, TAKESHI;YANAGI, RYOJI;AND OTHERS;REEL/FRAME:017780/0094;SIGNING DATES FROM 20051215 TO 20051219 Owner name: NIHON UNIVERSITY, JAPAN Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE 4TH INVENTOR'S EXECUTION DATE AND 1ST ASSIGNEE'S NAME AND TO ADD THE 2ND ASSIGNEE'S INFORMATION PREVIOUSLY RECORDED ON REEL 017631 FRAME 0249;ASSIGNORS:OKAI, KEIICHI;TAGASHIRA, TAKESHI;YANAGI, RYOJI;AND OTHERS;REEL/FRAME:017780/0094;SIGNING DATES FROM 20051215 TO 20051219 |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
FEPP | Fee payment procedure |
Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
FPAY | Fee payment |
Year of fee payment: 4 |
|
FPAY | Fee payment |
Year of fee payment: 8 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
LAPS | Lapse for failure to pay maintenance fees |
Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20210707 |